多支柱小车式起落架地面操纵特性研究

A Study of Ground Maneuver Stability of Multiple-Bogie Undercarriage

为研究采用多支柱小车式起落架布局的飞机在地面操纵特性并提出相关设计指标,建立了一套动力学分析模型,求出采用多支柱小车式起落架布局飞机的许用前轮偏转角的通解。通过仿真计算求得前轮许用偏转角度相关特性,通过试验验证了上述理论研究的正确性与合理性。经研究:多支柱小车式起落架许用前轮转弯角度主要受飞机速度等因素影响;在不改变飞机构型、不影响飞机性能及安全性的前提下,可通过降低飞机速度及减小前轮偏转角度提高飞机地面运动稳定性;在飞机速度一定时,将前轮偏转角度控制在许用包线内,则飞机转弯时不会发生侧翻;前轮转弯控制律设计过程中,可通过使控制律曲线尽量贴近许用包线以提高飞机地面操纵机动性。

To study characters of grouud maneuver of multiple-bogie undercarriage, set up a kinetic analysis model and find out the general solutions of allowable nose wheel steering angle. The test and simulations demonstrate that ground-maneuver stability of aircraft with multiple-bogie undercarriage could be improved by reducing aircraft＇s velocity and reducing nose wheel steering angle. When aircraft＇s velocity is given, aircraft roUover shall not occur on condition that nose wheel steering angle is within allowable nose wheel steering angle envelope. Aircraft＇s ground maneuver performance could be improved by getting nose wheel steering control law curve close to allowable nose wheel steering angle envelope.